| 动能拦截器助推段导引方案研究 |
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| 引用本文： | 郭庆,杨明,王子才.动能拦截器助推段导引方案研究[J].航空动力学报,2007,22(2):310-315. |
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| 作者姓名： | 郭庆 杨明 王子才 |
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| 作者单位： | 哈尔滨工业大学 控制与仿真中心, 哈尔滨 150001 |
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| 摘 要： | 针对大气层外高速飞行的目标, 提出了一种可用于动能拦截器助推段的导引方法.建立了拦截器和目标的运动模型, 在分析可拦截约束条件的基础上推导出转移轨道计算方法, 同时通过对拦截器可发射区域中的转移轨道优化得到满足约束条件的有效发射区域, 并以点火时刻待增速度为性能指标来寻优计算获得发射参数.仿真结果表明, 该方法能有效实现拦截器助推段的制导控制.
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| 关 键 词： | 航空、航天推进系统 动能拦截器 转移轨道 待增速度 发射参数 |
| 文章编号： | 1000-8055(2007)02-0310-06 |
| 收稿时间： | 2006/1/16 0:00:00 |
| 修稿时间： | 2006年1月16日 |
Research on kinetic kill vehicle's guidance method in boost phase |
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| GUO Qing,YANG Ming and WANG Zi-cai.Research on kinetic kill vehicle's guidance method in boost phase[J].Journal of Aerospace Power,2007,22(2):310-315. |
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| Authors: | GUO Qing YANG Ming and WANG Zi-cai |
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| Institution: | Control and Simulation Center, Harbin Institute of Technology, Harbin 150001, China |
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| Abstract: | A guidance method used in boost phase for intercepting the high-speed target in outer space was presented.After constructing the model of motion of the target and the kinetic kill vehicle(KKV),constraints of interception were analyzed and the computing method of orbit transfer was also derived.Then orbit transfer was optimized to get valid launching areas satisfying the constraints.Moreover,KKV's required velocity increase at firing time was selected as the specific performance index to optimize the computed launch parameters.Simulation results show that this method can implement efficiently KKV's guidance during the boost phase. |
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| Keywords: | aerospace propulsion system kinetic kill vehicle(KKV) orbit transfer required velocity increase launch parameters |
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